Replaceable thrust generating structures attached to an air vehicle

ABSTRACT

A replaceable thrust generating structure for an air vehicle, which includes one or more mounts, which are attachable to the air vehicle, and a thrust generating structure attached to each of the one or more mounts, and wherein the thrust generating structure includes an NMSET element.

CROSS REFERENCE

This application contains references to U.S. Provisional ApplicationNos. 61/239,446, filed Sep. 3, 2009, 61/264,778, filed Nov. 27, 2009,61/296,198, filed Jan. 19, 2010, and 61/448,610, filed Mar. 2, 2011, andPCT International Application No. US2010/002428, filed Sep. 3, 2010, theentire contents of which are hereby incorporated by reference herein.Priority is claimed to U.S. Provisional Application No. 61/448,610,filed Mar. 2, 2011.

TECHNICAL FIELD

The present disclosure is generally related to the field of thrustgenerating structures and, more particularly, is directed to replaceablethrust generating structures, which are attached to an air vehicle.

BACKGROUND

Devices for the movement of gases are widely utilized. The very firstaircraft engines were piston driven propellers. They worked by couplinga piston engine to a propeller. Their simplicity lead to widespreadadoption until jet engines were invented. Turbojet engines work by theprinciple of coupling a turbine to a fuel combination system. Spinningof the turbine compresses a fuel-air mixture which, when burned,provides thrust and torque to rotate the turbine. The first turbojetengines derived their thrust from exhaust leaving the engines. Modernvariants of the turbojet engines include turbo prop and turbofanengines, which use torque generated by the exhaust to drive a propelleror fan in addition to compressing the fuel-air mixture. Rocket enginesare possibly one of the oldest mechanical propulsion systems, and havenot changed much since their inception. A rocket comprises a tube orcone in which sits (or into which is fed) a fuel oxidizer mixture.Expanding gas from combustion of this mixture creates thrust. Rockets,while offering the highest fuel-thrust ratio of any existing propulsionsystems, cannot easily vary the amount of thrust they generate. Evenadding an ability to turn a rocket on or off significantly complicatesits design. Additionally, due to its complexity, damage to a propulsionsystem requires extensive work and expense to fix and/or replace.

Adhesion between two materials may be characterized into five types:mechanical, chemical, dispersive, electrostatic, and diffusive. Out ofthese five types, so far, only electrostatic and certain types ofmechanical adhesion are easily reversible processes. Vacuum may be usedto adhere surfaces and lift materials. However, such devices generallyrequire separate mechanisms for generating a reduced pressure andapplying the vacuum to a surface.

Generally, the conventional propulsion systems mentioned above can alsobe used to compress gas. It is also possible to compress gas via theideal gas law, such as in piston or diaphragm pumps. Current devicesgenerally require pumping apparatuses separate from a pressurizedvessel.

The ability of temperature differential to drive gas flow at a surfacehas long been known. In 1873, Sir William Crookes developed a radiometerfor measuring radiant energy of heat and light. Today, Crookes'sradiometer is often sold as a novelty in museum stores. It consists offour vanes, each of which is blackened on one side and light on theother. These are attached to a rotor that can turn with very littlefriction. The mechanism is encased inside a clear glass bulb with most,but not all, of the air removed. When light falls on the vanes, thevanes turn with the black surfaces apparently being pushed by the light.

Crookes initially explained that light radiation caused a pressure onthe black sides to turn the vanes. His paper was refereed by James ClerkMaxwell, who accepted the explanation as it seemed to agree with histheories of electromagnetism. However, light falling on the black sideof the vanes is absorbed, while light falling on the silver side isreflected. This would put twice as much radiation pressure on the lightside as on the black, meaning that the mill is turning the wrong way forCrooke's initial explanation to be correct. Other incorrect explanationswere subsequently proposed, some of which persist today. One suggestionwas that the gas in the bulb would be heated more by radiation absorbedon the black side than the light side. The pressure of the warmer gaswas proposed to push the dark side of the vanes. However, after a morethorough analysis Maxwell showed that there could be no net force fromthis effect, just a steady flow of heat across the vanes. Anotherincorrect explanation that is widely put forward even today is that thefaster motion of hot molecules on the black side of the vane provide thepush.

The correct explanation for the action of Crookes radiometer derivesfrom work that Osborne Reynolds submitted to the Royal Society in early1879. He described the flow of gas through porous plates caused by atemperature difference on opposing sides of the plates which he called“thermal transpiration.” Gas at uniform pressure flows through a porousplate from cold to hot. If the plates cannot move, equilibrium isreached when the ratio of pressures on either side is the square root ofthe ratio of absolute temperatures. Reynold's paper also discussedCrookes radiometer. Consider the edges of the radiometer vanes. The edgeof the warmer side imparts a higher force to obliquely striking gasmolecules than the cold edge. This effect causes gas to move across thetemperature gradient at the edge surface. The vane moves away from theheated gas and towards the cooler gas, with the gas passing around theedge of the vanes in the opposite direction. Maxwell also refereedReynolds' paper, which prompted him to write own paper, “On stresses inrarefied gases arising from inequalities of temperature.” Maxwell'spaper, which both credited and criticized Reynolds, was published in thePhilosophical Transactions of the Royal Society in late 1879, appearingprior to the publication of Reynold's paper. For more information on theCrookes radiometer, See, Philip Gibbs in “The Physics and RelativityFAQ—How a Light Mill works,” 2006, athttp://math.ucr.edu/home/baez/physics/General/LightMill/light-mill.html.

Despite the descriptions by Reynolds and Maxwell of thermally driven gasflow on a surface dating from the late 19th century, the potential formovement of gases by interaction with hot and cold surfaces has not beenfully realized. Operation of a Crookes radiometer requires rarefied gas(i.e. a gas whose pressure is much less than atmospheric pressure), andthe flow of gas through porous plates does not yield usable thrust,partially due to the thickness and due to the random arrangement ofpores in the porous plates.

SUMMARY

The inventive disclosure has particular utility when there are manysmall hard to service thrusters. While, generally, having a quick way toreplace a single large thrust producing device is unnecessary, whenthere are a plurality of small hard to service thrust producing devices,a quick and convenient way of replacing them is preferred. This allowsthe panels to then be refurbished by a more specialized team.

In accordance with an exemplary embodiment, a replaceable thrustgenerating structure for an air vehicle comprising: one or more mounts,which are attachable to the air vehicle; and a thrust generatingstructure attached to each of the one or more mounts, and wherein thethrust generating structure includes distributed thrusters. Thedistributed thrusters may be NMSET elements.

In accordance with a further exemplary embodiment, a method of using thereplaceable thrust generating structure, which includes exposing theapparatus to the source of ambient air at an ambient temperature andpressure and activating the means producing a gas pressure difference,such that the ambient air is propelled through the thrust generatingstructure.

The details of one or more embodiments of the disclosure are set forthin the accompanying drawings and the description below. Other features,objects, and advantages will be apparent from the description anddrawings, and from the claims.

BRIEF DESCRIPTION OF THE DRAWINGS

The present methods, devices and systems will now be described by way ofexemplary embodiments to which the invention defined by the claimsappended hereto are not limited. The details of one or more embodimentsof the disclosure are set forth in the accompanying drawings below.Other features, objects, and advantages will be apparent from thedescription and the drawings, and from the claims.

FIG. 1 shows a heat pump. This can be a Peltier slab, a slab driven bythermionic emission, or any other suitable means.

FIG. 2 shows gas flow patterns around the heat pump of FIG. 1.

FIG. 3 shows a gas confined in a square box with parallel hot walls andparallel cold walls.

FIG. 4 shows net forces on a stack of Nano Molecular Solid-stateElectrodynamic Thrusters (NMSET) with sawtooth geometry.

FIG. 5 shows gas particle velocities around a stack of NMSET withsawtooth geometry.

FIG. 6 shows the thermo-tunneling enhanced Peltier effect.

FIG. 7 shows a stack of NMSET with a parabolic geometry.

FIG. 8 shows gas flow patterns around the stack of NMSET of FIG. 7 andthe momentum space of the gas.

FIG. 9 shows a stack of NMSET with a triangular geometry.

FIG. 10 shows the momentum space of the gas around the stack of NMSETwith a triangular geometry.

FIG. 11 shows a stack of NMSET with a sawtooth geometry.

FIG. 12 shows the momentum space of the gas around the stack of NMSETwith a sawtooth geometry.

FIG. 13 shows a cross sectional view of an NMSET with an internalarrangement of solid state heat pumps. These heat pumps can be driven byPeltier effect, thermionic emission, or any other suitable means.

FIG. 14 shows a perspective view of NMSET with an internal solid stateheat pump arrangement on FIG. 13.

FIG. 15 shows a perspective view of an NMSET with an external solidstate heat pump arrangement.

FIG. 16 shows a cross sectional view of NMSET with an external solidstate heat pump arrangement of FIG. 15.

FIG. 17 shows a perspective view of NMSET with an external non-solidstate heat pump arrangement.

FIG. 18 shows a cross sectional view of a staged NMSET arrangement.

FIG. 19 shows NMSET with a straight geometry.

FIG. 20 shows an exemplary method of manufacturing NMSET.

FIG. 21 shows another exemplary method of manufacturing NMSET.

FIG. 22 is a side cross-sectional view illustrating a thermaltranspiration device.

FIG. 23 is a side cross-sectional view illustrating the operation of athermal transpiration device.

FIG. 24 is a side cross-sectional view of a thermal transpiration devicewith one extended layer and angled walls.

FIG. 25 is a top cross-sectional view of the thermal transpirationdevice illustrated in FIG. 24.

FIG. 26 is a side cross-sectional view of a thermal transpiration devicewith one extended layer and wet or dry etched walls.

FIG. 27 is a top cross-sectional view of the thermal transpirationdevice illustrated in FIG. 26.

FIG. 28 is a side cross-sectional view of a thermal transpiration devicewith two extended layers and angled walls.

FIG. 29 is a cross-sectional view of a beginning construction of oneembodiment of a thermal transpiration device.

FIG. 30 is a cross-sectional view of the continued construction of thethermal transpiration device shown in FIG. 29.

FIG. 31 is a side cross-sectional view of the continued construction ofthe thermal transpiration device shown in FIG. 30.

FIG. 32 is a cross-sectional view showing further construction of thethermal transpiration device shown in FIG. 31.

FIG. 33 is a cross-sectional view showing the islands formed in theconstruction of the thermal transpiration device.

FIG. 34 is a top view of an embodiment of a control system in accordancewith the present disclosure.

FIG. 35 is a top view of the control system illustrated in FIG. 34showing the operation of supplying power to a set of connection paths.

FIG. 36 is a top view of the control system illustrated in FIG. 34showing the effects of a fault in one of the power lines.

FIG. 37 is a top view of an embodiment of a control system in accordancewith the present disclosure that includes fault tolerance features.

FIG. 38 is a top view of another embodiment of the control system,designed to control larger arrays of distributed thrusters, than thecontrol system in FIG. 34.

FIG. 39 is top view of another preferred embodiment of the controlsystem, designed to control larger arrays of distributed thrusters thanthe control system in FIG. 38.

FIG. 40a is a top view of another embodiment of the present disclosure,showing primary and secondary affected areas when the control systemactivates the target area.

FIG. 40b is a cross sectional view of the embodiment shown in FIG. 40a ,with intersecting power lines located on the heated side of the device

FIG. 40c is another cross sectional view of the embodiment shown in FIG.40a , with intersecting power lines on each side of the device.

FIG. 41a is a top view of another embodiment of the present disclosurewith an electrical and or thermal insulator.

FIG. 41b is a cross sectional view of the embodiment shown in FIG. 41a ,with intersecting power lines located on the heated side of the device.

FIG. 42a is a top view of a grid structure for an array of distributedthrusters which includes a power supply line and a plurality of branchlines at the power line intersection point, to be used with the controlsystem.

FIG. 42b a top view of a middle insulating layer placed on top of FIG.42 a.

FIG. 42c is a top view a grid structure of a power supply line and aplurality of branch lines that is placed on top of FIG. 42b and createsa plurality of target points from a single power line intersection pointto be used with the control system.

FIGS. 43 and 44 are schematic diagrams for creating a temperaturegradient.

FIG. 45 is a plot showing a useful rise and fall in temperature in adevice having a temperature gradient.

FIG. 46 is a top cross-sectional view of a plurality of thruster regionsarranged in horizontal and vertical rows in accordance with the presentdisclosure.

FIG. 47 is a top cross-sectional view of a plurality thruster regionsshowing the heating effect of adjacent regions when a thruster region isactivated.

FIG. 48 illustrates an activation sequence for temperature gradientdevices among a plurality of temperature gradient devices in accordancewith the present disclosure.

FIG. 49 is a top view of one embodiment of an air vehicle with mountsfor thrust generating structures in accordance with the presentinvention.

FIG. 50 is a top view of an air vehicle with thrust generatingstructures attached to the mounts illustrated in FIG. 49.

FIG. 51 is a top view of an air vehicle with attached structurescontaining a nest for thrust generating modules in accordance with thepresent invention.

FIG. 52 is a top view of an air vehicle with attached structurescontaining multiple nests for thrust generating modules.

FIG. 53 is a top view of a further embodiment of a structure containinga nest for a thrust generating module in accordance with the presentinvention.

FIG. 54 is a side exploded view of a structure containing a nest for athrust generating module.

FIG. 55 is a side exploded view of a structure containing a nest for athrust generating module that is mounted flush to the surface of thestructure.

FIG. 56 is a top view of a thrust generating module with pressuresensors.

DETAILED DESCRIPTION

Overview

In preferred embodiments, one example of distributed thrusters, is anapparatus described herein that may be referred to as a Nano MolecularSolid-state Electrodynamic Thruster (NMSET). The basis of operation ofNMSET makes it possible to apply NMSET in the fields of, for example,propulsion, adhesion, compression and refrigeration, depending on themanner in which an NMSET is employed. In preferred embodiments, NMSETand related distributed thrusters devices provide lightweight, compact,energy-efficient creation of a gas pressure differential with adjustableflow velocity.

Propulsion

In some embodiments, distributed thrusters such as NMSET can offer oneor more of the following improvements in the field of gas propulsion:

1. Improved Resiliency: Damage to any area in a conventional gaspropulsion system would probably lead to system-wide failure.Distributed thrusters provide enhanced redundancy and robustness.

2. Lightweight: Electrically driven distributed thrusters, may make useof photovoltaic thin films, in which case fuel load vanishes.Furthermore since each thruster in a distributed thrusters systemcreates a local gas pressure difference, this local effect may requirefewer and or lighter apparatuses to maintain the structural integrity ofsuch gas propulsion system, than what would be normally required in anon-distributed gas propulsion system that generates the same gas flowvolume.3. Scalability: Conventional gas propulsion systems cannot be easilyscaled: optimal turbojets for small aircrafts are not scale reductionsof optimal turbojets for large aircrafts. Distributed thrusters areeasier to scale as scaling primarily changes the quantity of thrusterswhile leaving the individual thruster dimensions mostly intact.4. Response Time: Less massive thrust producing devices spool up anddown faster; as such, thrust from a distributed thruster gas propulsionsystem can be more easily adjusted in response to changes of need.5. Power Independence: Most conventional propulsion systems require aspecific type or class of fuels in order to operate, whereas someembodiments of distributed thrusters, such as, for example, NMSET, onlyrequires a source of temperature differential, which can generated byelectricity.6. Green Propulsion: Some embodiments of distributed thrusters, such asseveral embodiments of NMSET, expect an electrical input and as such, donot require fossil fuels to operate; therefore they do not producepolluting exhaust (e.g. carbon monoxide, nitrogen oxide) during ordinaryoperation when they use a non-polluting method of generating therequired electrical currents.

Adhesion

In some embodiments, distributed thrusters, such as, for example, NMSET,may be used as a lightweight mechanical adhesive that adheres to asurface through suction. The process can be reversible, as the only steprequired to reverse the adhesion is to cut power to the system in someembodiments. Using such a system can provide further benefit overelectrostatic adhesion in that such a system does not require a materialto be adhered to be flat or conductive, and does not leave behindresidue. Compared to other mechanical adhesion processes, using such asystem may not require a surface being adhered to be pretreated.

Gas Compression

Because distributed thrusters, such as, for example, NMSET, can bearranged to drive gas flow through a surface, all or part of apressurized vessel may function to provide gas compression. Thus, insome arrangements, separated pumping and pressurized containment may notbe required. Moreover, because, the action of such a system generallyoccurs over a short distance, it is possible, in some embodiments, touse such a system as a highly compact compressor by stacking multiplestages of distributed thrusters. Conventional gas propulsion systemsgenerally operate over length scales of centimeters and sometimesmeters. Thus, stacking conventional propulsion systems tends to be acomplex and expensive proposition. By contrast, distributed thrusterscan be packaged to operate over smaller scales, down to, for example,micrometers. Furthermore, the versatility of such systems means thatsuch a system can be readily adapted to function as a high-pressurepump, a standard atmospheric pump, or with a sufficient number ofstages, as a high vacuum pump.

NMSET Design

In one aspect and embodiment, NMSET and some related devices describedhere may be thought of as functioning by reducing entropy in gas incontact with the system. Optionally, such device may add energy, inaddition to the energy lost through inefficiencies in the system, e.g.thermal energy, to the gas. In another aspect and embodiment, thegeometry of NMSET and some related devices can affect gas flow directionand convenience of use. Several embodiments of NMSET and some relateddevices may be further distinguished from previous thermal transpirationdevices and the like by the combined application of scale parameters,materials having advantageous molecular reflection properties,geometries, design, construction and arrangement of elements thatprovide significant increase in efficiency, and or capabilities tooperate at higher ambient pressures and/or produce higher flow rates.Described herein are various exemplary embodiments of NMSET withdiscussion of these and other parameters that, in preferred embodiments,can create a strong gas flow in a particular direction with minimalthermodynamic loss, and or operate at higher ambient pressures and orproduce higher flow rates.

Reduction of entropy in a gas by NMSET may be represented by atransformation A in the momentum space k of the gas. A can be expressedin a matrix once a set of suitable bases is chosen for the momentumspace k. If the expectation value of the transformed momentum space Akis nonzero, the NMSET receives a net momentum in the opposite directionof the expectation value due to the conservation of momentum.

The geometry of NMSET may be optimized for more efficient functioning.The geometry of NMSET affects the transformation matrix A. A geometrythat produces a matrix A essentially equal to an identity matrix I doesnot create a net momentum bias (i.e. will not make the transformedmomentum space Ak have a nonzero expectation value). Rather, gasvortexes may be generated. Geometries that result in larger eigenvaluesof A tend to imply a more efficient function, e.g., that more momentumis carried by gas particles moving in a particular direction.

As an example, consider a heat pump 100 immersed in a gas, shown inFIG. 1. The heat pump 100 comprises an upper layer 101 and a lower layer102. For simplicity, a Cartesian coordinate system can be referencedwith a y-axis pointing from the lower layer 102 to the upper layer 101.A temperature differential can be established by a Peltier device (notshown) between the layers or any suitable means such that the upperlayer 101 is colder than the gas and the lower layer 102 is hotter thanthe gas. For sake of simplicity, one may assume that the heat pump 100has 100% Carnot cycle efficiency. However, other efficiencies arecontemplated. In this case, the heat pump 100 will not transfer net heatinto the gas. Transformation caused by the heat pump 100 to the momentumspace k of the gas can be expressed by a Hermetian matrix A. When a gasparticle (molecule or atom) collides with the lower layer 102, assumingthe collision is diabatic, the gas particle rebounds off at a highervelocity than before the collision. When a gas particle collides withthe upper layer 101, assuming the collision is diabatic, the gasparticle rebounds off the upper layer 101 at a reduced velocity thanbefore the collision. The heat pump 100 feels a net force in the ydirection. In other words, the lower layer 102 heats and thus increasespressure of the gas below the lower layer 102, while the upper layer 101cools and thus decreases the pressure of the gas above the upper layer101. The pressure difference exerts a force on the heat pump 100 in they direction. In terms of transformation of the momentum space k of thegas, as gas particles rebounding from the upper layer 101 leave withless momentum than gas particles rebounding from the lower layer 102,the transformed momentum space Ak becomes skewed preferentially in the−y direction, i.e., the expectation value p of the transformed momentumspace Ak is nonzero and points to the −y direction. Assuming the gas andthe heat pump 100 compose a closed system (i.e., no interaction withother objects), the heat pump 100 gains a momentum −p to conserve thetotal momentum of the closed system.

While the geometry of the heat pump 100 in FIG. 1 does generate adirection force, in certain circumstances it may not be practical forthe following reasons:

1. If the heat pump 100 is large, translational motion of the heat pump100 along the y direction forces the gas to flow all the way aroundedges of the heat pump.

2. The vast majority of the heat is transferred from surfaces of theheat pump 100 via gas convection.

3. Gas near the surfaces has an insulating effect. Momentum transferbetween the heat pump 100 and the gas is not efficient except inproximity of the edges of the slab, as shown in FIG. 2.

4. Surface area of the heat pump 100 is surface area of its convex hull.

These problems all relate to a single core issue, very little of the gashas any direct surface contact. Thus, a more complex geometry can beadvantageous. Exemplary embodiments with three different geometries aredescribed herein.

Principles of Operation

Although many different geometries of NMSET or related devices arepossible, the principle of operation of NMSET remains the same. Whilenot wanting to be limited to any particular theory, operation usesenergy to reduce entropy on some device surfaces and transfer reducedentropy to a gas in contact with the surface. The device can optionallydonate energy to the gas by raising the gas temperature. The function ofNMSET may be therefore divided into three areas: the means by whichentropy on surfaces of the device is reduced, the means by which thereduced entropy is transferred to the gas, and the optional means otherthan the inefficiency of the Carnot cycle of the heat pump by which thegas temperature is increased.

Temperature Differential

A temperature differential between layers of material or more precisely,between two opposing surfaces is generally required for NMSET or relateddevice to operate. In preferred embodiments described herein, atemperature differential can be established in a solid-stateelectrodynamic mechanism, i.e., the “SE” of NMSET. However, the devicesand methods described here are not limited to electronic or purely solidstate devices. For example, a temperature differential may beestablished by conduction of heat from combustion using a fluid coolant,exothermic chemical reaction, or other chemical source. A temperaturedifferential may be established by simple resistive heating, by thePeltier effect, by thermionic emission, by the thermo-tunneling enhancedPeltier effect, or by any other suitable means, such as explained below.A means by which the temperature differential is established between twoobjects can be phenomenologically described by two characteristics:entropy-reduction (heat transfer between the two objects), anddiabaticity (total heat transfer between environment and the twoobjects).

In one embodiment, the Peltier effect can be used to establish atemperature differential. The Peltier effect occurs when an electriccurrent is applied through a loop composed of two materials withdifferent Peltier coefficients joined at two junctions. Depending on thedirection of the electric current, heat flows from one junction to theother, causing a temperature differential to be established between thejunctions. The Peltier effect can be understood as follows: Heatcapacity of charge carriers in a material is characterized by thePeltier coefficient Π, which is the amount of heat carried per unitcharge carriers in the material. When an electric current I flowsthrough a junction of material A with Peltier coefficients Π_(A) andmaterial B with Peltier coefficient Π_(B), the amount heat carried bycharge carriers to the junction in a unit time is I×(Π_(A)−Π_(B)).

An ideal Peltier effect reduces entropy locally and is adiabatic.Assuming Joule heating and or Carnot cycle inefficiencies can beignored, in the Peltier effect, heat is transferred from one junction toanother, but no heat is added into the loop of the two materials. Thisentropy reduction can provide for advantages in the stackability ofNMSET and related devices. Consequently, the Peltier effect lends itselfparticularly well to some embodiments.

In this embodiment, a power source drives an electric current betweentwo surfaces. Charge carriers such as electrons and/or holes carry heatas they flow in the electric current, and thus create a temperaturedifferential between the two surfaces. Entropy is reduced as thetemperature differential is established.

Phonon flow reduces the temperature differential established by thePeltier effect. If phonons are permitted to flow freely (i.e., infinitethermal conductivity or zero heat capacity), their flow will cancel thetemperature differential established by the Peltier effect. Efficiencyof the Peltier effect can be increased by reducing electrical resistanceand thermal conductance.

One way to reduce thermal conductance is to place a narrow vacuum gap inthe path of the electric current. Phonons cannot easily pass the vacuumgap but charge carriers can do so under a voltage across the vacuum gap.This is called thermo-tunneling enhanced Peltier effect (or thermotunnelcooling). FIG. 6 shows a diagram of the thermo-tunneling enhancedPeltier effect. Charge carriers 601 can tunnel through a vacuum gap 602.

The thermo-tunneling enhanced Peltier effect is generally onlysignificant at high temperatures or voltages, unless enhanced by choiceof surface geometry and materials that can restrict behavior of chargecarriers near the vacuum gap and increase tunneling probability. Forexample, suitable surface coatings and structures can function as afilter that do not allow low energy states of charge carriers but onlyhigh energy states of charge carriers near the vacuum gap.

In another embodiment, a temperature differential can be created andmaintained by field-enhanced thermionic emission. Thermionic emission isa heat-induced flow of charge carriers over a potential-energy barrier.The charge carriers can be electrons or ions (i.e., thermions). In asimple approximation, the potential-energy barrier acts like a dam, inthat it withholds carriers with thermal energy less than its height andallows carriers with thermal energy greater than its height to flowover. When the overflowing carriers pass the potential-energy barrier,heat is carried away with them. The carriers left behind thepotential-energy barrier re-thermalize (redistribute in energy) to alower temperature. Thermionic emission typically requires an operatingtemperature of several hundred degrees Celsius so that a non-negligiblefraction of the carriers has thermal energies great enough to overcomethe potential-energy barrier. An electrical field can assist thermionicemission by reducing the height of the potential-energy barrier andreducing the required operating temperature.

A temperature differential in NMSET or related device can also beestablished by using resistive heating (explained below) and/or bysuitable chemical processes. In order to maintain the temperaturedifferential without raising the overall temperature of the device, somecooling means can also be provided, such as a heat sink exposed toatmosphere. No matter what cooling means is used, the temperaturedifferential is more pronounced if warmer surfaces of the device are notcooled as efficiently as cooler surfaces, which can be achieved, forexample, by thermal insulation.

Force Generation

In one aspect, the production of net thrust may be thought of as thetransfer of the reduced entropy from an established temperaturedifferential to a gas. Without wishing to be bound by theory, consider asingle device operating in a gas, as an adiabatic process. In thisexample, a temperature differential between a hot and a cold layer canbe established by a suitable means such as the Peltier effect. Forsimplicity, assume no net heat transfer between the gas and the device.Particles of the gas will impact the hot and cold layers with equalprobabilities, and their interaction with these layers will haveconsequences on local momentum space of the gas near surfaces of the hotand cold layers. The local momentum space of the gas very close to asurface of the hot and cold layers has nonzero expectation value whenthe gas and the surface have different temperatures. Assuming also thatno gas particles penetrate the surface, the gas particles rebound fromthe surface with momenta different from their incident momenta, whichskews the momentum space along the surface normal, and the magnitude ofthe skew is directly related to the temperature difference between thesurface and the gas.

In an arrangement with random geometry (i.e. surface normals atdifferent surface locations point to random directions), the weightedsum of expectation values of local momentum spaces of the gas is nearlyzero, which results in almost no net thrust. In NMSET with an optimizedgeometry, however, the weighted sum of expectation values of localmomentum spaces of the gas can be non-zero, which leads to a net thrust.

A trivial example of an arrangement that has non-zero net thrust isshown in FIG. 1, as described above. This geometry is not very efficientbecause macroscopic convective gas flows and vortex formation increasethe entropy and limit the amount of useful work. Exemplary convectivegas flows 120, 130 are shown in FIG. 2. Gas at ambient temperature 110flows towards the cold layer 101 and gets cooled. Cooled gas flows 120away from the cold layer 101 and around the edge of the heat pump 100towards the hot layer 102. Heated gas flows 130 away from the hot layer102.

To simplify the description, it may be helpful to think about the systemin terms of Newton's second law and the kinetic theory of gases. Aroundthe heat pump 100 in FIGS. 1 and 2, assuming that temperature of the gasis bracketed by the temperatures of the layers 101 and 102, gasparticles that collide with the layer 102 leave the layer 102 withgreater momentum than before the collision. Similarly, gas particlesthat collide with the layer 101 leave the layer 101 with lesser momentumthan before the collision. Since gas pressure is directly related tomomenta of gas particles, gas near the layer 102 has higher pressurethan gas near the layer 101. This pressure bias pushes the entire heatpump 100 in the y direction.

In another embodiment, the heat pump 100 can have at least one throughhole between the layer 101 and 102. Gas spontaneously flows from thelayer 101 to the layer 102 through the hole which enables higher heatingrate of the gas. Such preferential flow of gas is referred to as thermaltranspiration. Assuming gas near the layer 101 has temperature of T_(c)and pressure of P_(c), and gas near the layer 102 has temperature ofT_(h) and pressure of P_(h), thermal transpiration causes the gas toflow from the layer 101 to the layer 102 through the hole, if thefollowing equation is satisfied:

$\begin{matrix}{\sqrt{\frac{T_{h}}{T_{c}}} \geq \frac{P_{h}}{P_{c}}} & \lbrack 1\rbrack\end{matrix}$

In order to improve efficiency, it is helpful to understand where theclassical limit exists within gas flows. Convective descriptions of gasflow break down at around length scales where the Knudsen numberappears. As a result, in some aspects, the mean free path of a gasbecomes a useful parameter in determining advantageous geometries ofNMSET.

For instance, consider a gas at a particular pressure having a mean freepath of 10 nm. If a cloud of such gas is trapped in a two dimensionalsquare 20 nm by 20 nm box as shown in FIG. 3, a gas particle, within 10nm of travel, will be approximately as likely to have struck another gasparticle as it is to have struck the walls of the box. If the walls ofthe box are heated, then smaller boxes will reach thermodynamicequilibrium with gas therein faster than larger boxes, because gasparticles in smaller boxes have more chances to collide with andexchange heat with the walls. Generally, when most of collisions in agas are between gas particles and a surface, then thermodynamicequilibrium can be achieved approximately in the mean free time (thetime it takes a gas particle to travel the mean free path).

For this reason, in some embodiments, the characteristic scale ofindividual features of NMSET and related devices may be nanoscale, i.e.,the “NM” of NMSET. However, it must be understood that the methods anddevices described here are not limited to nanoscale embodiments. Themean free path parameter is dependent on gas density so that in someembodiments and uses, larger scale features may be employed.Furthermore, as described herein, pluralities of NMSET and relateddevice elements can be combined to provide action over a large surface.For example, distributed thrusters such as NMSET may advantageously bearranged in arrays and or arrays of arrays to provide directed movementof gas over across large surfaces, for example, as illustrated in FIGS.15, 16 and 17. Distributed thrusters such as NMSET can also be arrangedin one or more stages to achieve a greater pressure differential, forexample as illustrated in FIGS. 18A-18D. FIG. 18A illustrates a crosssectional view of an array of staged distributed thrusters such as NMSETarrangements 1800. Each staged arrangement 1800 is composed of stages1810, 1820, 1830 of in the form of concentric half-spheres containingarrays of distributed thrusters such as NMSET 1840, 1850, 1860illustrated in blow-up in FIGS. 18B-18D. Individual distributed thrusterapertures 1845, 1855, 1865 in each stage increase in optimal size andthickness in accordance with the decreasing ambient pressure that wouldbe experienced at each previous stage in operation.

Surface Interaction

Interaction between surfaces can affect the momentum spacetransformation matrix A. If nearby surfaces can easily exchange phononsvia gas particles, then the entropy at these surfaces will locallyincrease at a higher rate than surfaces which cannot easily exchangephonons via development of vortexes. This will generally reduce theefficiency of a system.

One method by which phonon exchange may be reduced is to limit oreliminate any shared bases between surfaces. For instance, consider gasparticles in the box 300 in FIG. 3. Box 300 comprises two planar hotwalls 302 parallel to each other, and two planar cold walls 301 parallelto each other and perpendicular to the hot walls 302. If the box 300 iscomparable in size to the mean free path of the gas particles thereinand the walls 301 and 302 are perfectly specular, the gas particles canreach thermal equilibrium with the cold walls 301 and the hot walls 302independently. This is because surface normals of the walls are onlyshared between the two cold walls 301 or between the two hot walls 302,but not between a cold wall 301 and a hot wall 302. Consequently, littleto no momentum can be exchanged between the hot walls 302 and the coldwalls 301 by the gas particles. This is because interaction between thegas particles and the cold walls 301 only affect momenta in the xdirection but not momenta in the y direction; and interaction betweenthe gas particles and the hot walls 302 only affect momenta in the ydirection but not momenta in the x direction and the fact that momentain the x direction are orthogonal with momenta in the y direction,assuming no collisions between gas particles. After thermal equilibriumis reached between the gas particles and the walls, the gas particlesmove faster in the y direction than in the x direction.

As a practical matter, surfaces are usually not perfectly specular.However, specular surface properties exist very strongly in somematerials so that there are angles for which convective flows in cornersmay be reduced. This effect is generally observed when the Knudsennumbers are large, which is a preferred condition for NMSET and relateddevices, particularly in nanoscale embodiments. The Knudsen number (Kn),named after Danish physicist Martin Knudsen (1871-1949), is adimensionless number defined as the ratio of the molecular mean freepath to a representative physical length scale. In NMSET or the relateddevices discussed here, the representative physical length scale istaken to be the order of magnitude of the aperture diameter of thedevice, i.e., the representative physical scale length is, for example,a nanometer if the aperture is measured in nanometers, and a micrometerif the aperture is measured in micrometers. In preferred methods ofusing the devices disclosed herein the Knudsen number is preferablygreater than 0.1, or greater than 1, or greater than 10.

Methods of Optimizing NMSET and Related Devices

Modeling

Performance of NMSET with a specific geometry can be simulated by aMonte-Carlo method for optimization. Specifically, a simulation forNMSET or related device with any given geometry starts with a group ofgas particles with random initial positions and momenta around thedevice. Positions and momenta of these particles after a small timeinterval are calculated from the initial positions and momenta, usingknown physical laws, parameters such as temperature, pressure, chemicalidentity, geometry of the device, interaction between surfaces of thedevice and the gas particles. The simulation is run through a chosennumber of iterations and simulation results are analyzed. The geometryof the device can be optimized using simulation results. In preferredembodiments, a device is constructed using the results of the simulationanalysis.

In a preferred embodiment, a simulation can be represented in thefollowing table:

Algorithm 1 EVOLVE MODEL(M, P, k) M←0 P←a set of search parametersk←number of iterations for i = 1 to k do V←An instance of P V←Vperturbed by M E←MONTE CARLO(V) Update M using E end for

A perturbation model M is evolved through a number (k) of iterations.First, M is initialized to an empty set, indicating no solutionknowledge. Then, a loop is started in which the search parametersgenerate an arbitrary element from the definite search space P and theprior learned knowledge M is used to perturb P. The specific algorithmused to perturb as an implementation detail.

If run in a grid computing environment, M should ideally be identicalamong all nodes, but this is not necessary due to the inherentlystochastic nature of the process. The step of EVOLVE_MODEL whichactually runs the Monte-Carlo simulation is the most computationallyexpensive of all by far and offers a lot of time to synchronize M.

Specific parameters depend on the environment. The parameters that theuser can specify include the following:

1. Molecular diagrams, in some embodiments containing up to three atoms,such as CO₂ or H₂O.

2. Partial concentrations for constituent molecules.

3. Initial temperature and pressure of the entire gas.

In a stationary simulation, the Monte-Carlo simulation can be run withperiodic bounds in all axes. In the y axis, however, particlesencountering the periodic bound are stochastically thermostattedaccording to temperature and pressure settings in order to simulateambient conditions. In the x axis, particle velocities are unmodified inorder to simulate a periodic ensemble of identical device assembliesalong that direction. The simulation may be run in two dimensions toreduce the computational complexity of the simulation. A threedimensional simulation should give similar results where the modeleddevice has cylindrical symmetry. Note that in general, a simulator doesnot have to use the periodicity as indicated here and may not specifyany boundaries at all; they are only defined as a computationalconvenience.

In preferred embodiments, potential device geometries can be evaluatedin consideration of the conditions under which a device will be used andknown surface reflection properties of the material from which it willbe constructed. Geometrical parameters can be optimized by analyzingresults from simulation before the geometry is actually used inmanufacture of NMSET and related devices.

Example Geometries

Four embodiments with different geometries are particularly discussedbelow. These four geometries will be referred to as Straight, Parabolic,Triangular, and Sawtooth. It must be noted that the geometries of theNMSET and related devices described here can vary considerably and theseexamples should be taken only as illustrations for the purpose ofdiscussing the effects of certain design choices on system efficiencies.

Straight

FIG. 19 shows an embodiment of NMSET or related device 1900 with astraight geometry. In this embodiment, the device 1900 comprises a hotlayer 1902 and a cold layer 1901. The terms “hot layer” and “cold layer”mean that these layers have a temperature difference therebetween, notthat the “hot layer” is necessarily hotter or the “cold layer” isnecessarily colder, than a gas that NMSET or related device is immersedin. At least one straight through hole 1910 extends through all layersof the device 1900 and preferably has a similar cross-sectional shapeand size for each set of layers. The straight through hole 1910 can haveany cross-sectional shape such as circular, slit, and comb.

Preferably, a total length 1910L (i.e. a distance from one entrance tothe other entrance) of the straight through hole 1910 is up to 10 times,up to 5 times or up to 2 times of the mean free path of a gas in whichthe device 1900 is immersed. The mean free path of air at the standardatmosphere pressure is about 55 nm. At higher altitude, the mean freepath of air increases. For atmospheric applications, the total length1910L is preferably not greater than 1500 nm, and depending onapplication more preferably not greater than 550 nm, not greater than275 nm or not greater than 110 nm. A temperature differential betweenthe hot layer 1902 and the cold layer 1901 is preferably at least 0.5°C., more preferably at least 30° C., more preferably at least 50° C.,and most preferably at least 100° C.

The hot layer 1902 and the cold layer 1901 may be separated by a gaptherebetween for thermal isolation. The gap preferably is a vacuum gapand/or contains a thermal insulator. In one example, the gap contains aplurality of thin pillars made of a good thermal insulator such assilicon dioxide.

The device 1900 has preferably at least 10 straight through holes persquare centimeter. A total perimeter length of all the straight throughholes of the device 1900 per square centimeter is preferably at leasttwo centimeters.

Parabolic

FIG. 7 shows an embodiment of an NMSET or related device 700 with aparabolic geometry. In this embodiment, alternating hot layers 702 andcold layers 701 are stacked. In the illustration, each hot layer 702 andcold layer 701 has a straight through hole. All the holes are aligned.The hole in each hot layer 702 has the similar size as the hole in thecold layer 701 immediately above, and is smaller than the hole in thecold layer 701 immediately below. Each cold layer 701 is colder than itsimmediate adjacent hot layers 702 and each hot layer 702 is hotter thanits immediate adjacent cold layers 701. A surface 702 a of each hotlayer 702, which has a surface normal in the −y direction, is exposed.All the holes collectively form a nozzle with a contour of a parabolicsurface. This geometry minimizes shared bases between the hot and coldlayers. However, because NMSET or related device may not substantiallyincrease the energy of the gas, the increasing hole diameter may resultin a drop in gas pressure at the edges. This can create strong vortexesnear the lower aperture, which reduce total efficiency. NMSET with theparabolic geometry can be adiabatic or isobaric, but not both. Anapproximation of gas flow in NMSET or related device with the parabolicgeometry is shown in FIG. 8. The momentum space of the gas is skewedsuch that the expectation value of the momentum points to the −ydirection.

Although the parabolic geometry is effective in NMSET or related device,a drop in gas pressure puts an upper bound on the size of the loweraperture. In general, any adiabatic device in which the gas being movedundergoes a change in volume will suffer in its efficiency.

If the temperature differential in a device with the parabolic geometryis established by a diabatic means (i.e. the device raises the overalltemperature of the gas), then the NMSET with the parabolic geometry maynot suffer in its efficiency from the gas undergoing a change in volume,as long as the amount of heat added to the gas is sufficient to preventthe formation of vortexes. However, such a device suffers in itsefficiency from higher total entropy, i.e., the eigenvectors of themomentum space of the gas are not as far apart if the gas has to expand,but supplying heat at small scales is typically easier than carrying itaway.

Triangular

The triangular geometry detailed in FIG. 9 is a partial optimization ofthe parabolic geometry for adiabatic flows. In this case, the gas is notpermitted to experience a sufficient expansion to trigger large-scalevortex generation. Furthermore, because the apertures do not changesize, a triangular arrangement such as this one may be easily stacked.

The momentum space of this triangular geometry is more efficientlybiased, as is illustrated in FIG. 10. As in the parabolic arrangement,the exposed hot and cold surfaces meet at preferably a 90-degree angle;however, a source of inefficiency arises when particles carry heat backand forth between surfaces across the center gap.

FIG. 9 shows a stack 900 of NMSET or related device with the triangulargeometry. Each device in the stack 900 comprises a hot layer 902 and acold layer 901 of equal thickness. The temperature differential betweenthe cold and hot layers 901 and 902 can be established by any suitablemeans such as the Peltier effect or any other heat pump. Each device hasa through hole 903. Each though hole 903 has approximately a 45° chamfer(9031 and 9032) on each entrance. The surface of the chamfers 9031 and9032 is, for example, from 1.40 to 1.42 times of the thickness of thecold and hot layers 901 and 902, not including modifications to theacute angles for structural considerations. The through holes 903 in alllayers in the stack 900 are aligned. In general, the temperatures of thehot layers 902 in a device in the stack 900 do not increasemonotonically from one side of the stack to the other side. In general,the temperatures of the cold layers 901 in a device in the stack 900 donot decrease monotonically from one side of the stack to the other side.Preferably, each cold layer 901 is colder than its immediate adjacenthot layers 902 and each hot layer 902 is hotter than its immediateadjacent cold layers 901. For engineering reasons, the hot and coldsurfaces of the triangular arrangement may not come to a fine point.

Sawtooth

FIG. 11 shows a stack 1100 of NMSET or related device with a sawtoothgeometry. Each device in the stack 1100 comprises a hot layer 1102 witha thickness of t_(h) and a cold layer 1101 with a thickness t_(c). Thetemperature differential between the cold and hot layers 1101 and 1102can be established by any suitable means such as the Peltier effect orany other heat pump. Each device has a through hole 1103. In theillustrated device, each through hole 1103 has a chamfer 11031 at theentrance on the side of the cold layer 1101, and a chamfer 11032 at theentrance on the side of the hot layer 1102. An angle between the chamfer11031 and a center axis of the through hole 1103 is θ₁; an angle betweenthe chamfer 11032 and a center axis of the through hole 1103 is θ₂. Thesum of θ₁ and θ₂ is preferably from 75° to 105°, more preferably from85° to 95, and more preferably from 88° to 92°. The ratio of t_(c) tot_(h) is substantially equal to the ratio of cotangent of θ₁ tocotangent of θ₂. θ₂ is preferably from 70° to 85°.

The relationships of the chamfer angles described here are preferredlimitations, not hard boundaries. In general for materials exhibitperfectly specular molecular reflection properties, the relationships ofthe chamfer angles can be slightly relaxed. For materials exhibit lessthan perfectly specular molecular reflection properties, therelationships shall be stringent. The chamfer geometries are preferablyarranged so as to minimize shared bases. The surface normals of thespecularly reflecting chamfer surfaces can thus preferably beorthogonal. Deviations from orthogonality can incur a penalty inefficiency as a cosine function. For engineering reasons, the hot andcold surfaces of the sawtooth arrangement may not come to a fine point.

In the illustrated device, the through holes 1103 in all layers in thestack 1100 are aligned. Temperatures of the hot layers 1102 in eachdevice in the stack 1100 do not increase monotonically from one side ofthe stack to the other side. Temperatures of the cold layers 1101 ineach device in the stack 1100 do not decrease monotonically from oneside of the stack 1100 to the other side. Each cold layer 1101 is colderthan its immediate adjacent hot layers 1102 and each hot layer 1102 ishotter than its immediate adjacent cold layers 1101.

The sawtooth geometry shown in FIG. 11 offers an improvement over thetriangular geometry in that all hot layers 1102 are preferably orientedin nearly the same direction (i.e., θ₂ is preferably nearly 90°). Thisreduces direct interaction between hot and cold layers 1102 and 1101across the through hole 1103, and improves overall efficiency.

Furthermore, because the hot layers 1102 have a lower exposed surfacearea than the cold layers 1101, and because the cold layers 1101 arepreferably oriented at a shallower angle relative to the center axis ofthe through hole 1103 than in the triangular geometry, the sawtoothgeometry is capable of reducing the entropy in the gas (and therebycausing it to do more work) more efficiently than the triangulargeometry. The momentum space of this sawtooth geometry is moreefficiently biased than the momentum space of the triangular geometry,as is illustrated in FIG. 12.

In the triangular configuration, device slices on opposite sides of across section have a magnitude of 1/√{square root over (2)} in the yaxis because their separation angle 90 degrees. This limits theefficiency of entropy reduction, as some of the entropy is going to beneutralized in direct inter-surface interaction.

In the sawtooth configuration, however, the hot layers 1102 not onlyshare no basis with the adjacent cold layers 1101, but also share verylittle basis with hot and cold layers across the through hole 1103. Thiscombined property makes the sawtooth geometry more efficient than thetriangular geometry.

After NMSET or related device is powered (i.e. temperature differentialis established), gas particles rebounding from cold layers have areduced net velocity, while gas particles rebounding from hot layershave higher net velocity. FIG. 4 shows net forces the layers of thestack 1100 (sawtooth geometry) experience. In a stable state, lowpressure is generated at the entrance aperture (upper aperture in FIG.4) which in turn generates a corresponding low-pressure region above thestack 1100, and a high-pressure region below the stack 1100. Gasparticle velocities of the stack 1100 resulting from the gas particlecollisions are shown in FIG. 5.

Means for Establishing Temperature Differential

Internal Peltier

According to one embodiment, each element in the device geometry actsboth as a particle director and as the entropy reducer. In a Peltierdevice, the hot and cold plates are made of materials with differentPeltier coefficients. Electrical current is made to flow between thecold and hot plates. This flow of current carries with it Peltier heat,establishing the temperature differential necessary to operate thedevice. In some embodiments, piezoelectric spacers can be disposedbetween device elements to maintain the separation gaps therebetween.

A cross section of NMSET or related device according to an embodimentwith an internal Peltier arrangement is detailed in FIGS. 13 and 14. Allhot layers 1302 are connected. All cold layers 1301 are connected.Electric current flows through a Peltier device interposed between thecold and hot layers to establish a temperature differential. The thinnerthe layers are, the higher the electric current is necessary.

NMSET or related device with the internal Peltier arrangement can makeit easier to reduce the size of the device. A single stack such as theone shown in FIG. 14 can be fully functional to generate thrust. NMSETor related device with the internal heat pump are further suitable foruse in microelectromechanical systems (MEMS) that emphasize the highestdegree of granularity.

Field-Enhanced Thermionic Emission

In another embodiment, the temperature differential can be generated byfield-enhanced thermionic emission. As shown in FIG. 19, an electricalfield can be established between the layers 1901 and 1902 such thatcharge carriers thermally emitted from the cold layer 1901 carry heatfrom the cold layer 1901 to the hot layer 1902.

External Peltier

In another embodiment, the temperature differential can be generated bya heat pump, such as a Peltier device external to NMSET or relateddevice. This Peltier device arranged in a checker board fashion isthermally coupled to NMSET or related device stack 1500 via interfacelayers 1510 and 1520 as detailed in FIGS. 15 and 16.

A device with an external Peltier device has the benefit of separatingthe materials used to generate gas flow from the materials used togenerate the temperature differential. From an engineering standpointthis may be desirable, as the materials suitable for a heat pump may notbe suitable for microstructures, or vice versa. In addition, an externalheat pump can be made larger and more efficient, and may require lesscurrent to establish a sufficient temperature differential.

Piezoelectric spacers can be used between layers. Materials suitable foruse in NMSET preferably are strong enough to mechanically withstandthermal expansion and contraction, and/or preferably have very smallexpansion coefficients. Otherwise, holes in the layers could becomemisaligned, which could reduce efficiency.

External Non-Peltier

According to yet another embodiment, a temperature differential isestablished by any suitable heat source and/or heat sinks. For example,the heat sources might be field-enhanced thermionic emission, resistiveheaters, chemical reaction, combustion, and/or direct illumination ofbright light or other forms of radiation. An illustration of such anembodiment is shown in FIG. 17. In the example shown, a heating surface1702 can be resistive heating material, or a material that canefficiently receive radiative heating. The external non-Peltier heatpump is convenient because it does not require a built in heat pump suchas a Peltier device. For some applications, it may be convenient todirect the heating surface towards a source of radiation, such as thesun, rather than first converting radiation into electricity and drive aheat pump. Alternatively, a source of radiation may be directed toward aheat absorbing surface in thermal communication with the hot layer ofNMSET or related device. In an external non-Peltier heat pump, however,more care is preferably taken to ensure that the NMSET or related devicedoes not overheat.

The capillaries 1750 illustrated in FIG. 17 provide an exemplarymechanism by which a heat sink could be provided; however, it is alsopossible for the heat sink to simply be a series of vanes, or any othersuitable heat sinks. Alternatively, the external non-Peltier heat pumpin FIG. 17 could be configured to provide a heat source through thecapillaries 1750. The heat source can be an exothermic chemicalreaction, preferably one that does not generate too much pressure.

Materials

NMSET and related devices may be constructed of a wide range ofmaterials. In various aspects, properties of materials may be exploitedin combination with desirable geometries.

Specular reflection of gas molecules is a preferred property of thematerials which form the gas-exposed surfaces of NMSET or relateddevice, e.g. the heated and cooled surfaces which are in contact withflowing gas. Specular reflection is the mirror-like reflection of light,or in this case gas particles, from a surface. On a specular surface,incoming gas particles at a single incident angle are reflected from thesurface into a single outgoing angle. If the incoming gas particles andthe surface have the same temperature, the incident angle and theoutgoing angle with respect to the surface normal are the same. That is,the angle of incidence equals the angle of reflection. A second definingcharacteristic of specular reflection is that incident, normal, andreflected directions are coplanar. If the incoming gas particles and thesurface are not at the same temperature and the reflection is diabatic(i.e. with heat exchange between the gas particles and the surface), theangle of reflection is a function of heat transferred between thesurface and the gas particles.

The degree of specularity of a material may be represented by areflection kernel (such as the Cercignani-Lampis kernel) which isdefined as the probability density function of reflected state of thegas particles per unit volume of the phase space. Details of thereflection kernel are disclosed in “Numerical Analysis of Gas-SurfaceScattering Effect on Thermal Transpiration in the Free MolecularRegime”, Vacuum, Vol. 82, Page 20-29, 2009, and references citedtherein, all of which are hereby incorporated by reference.

Individual hot and cold layers may also be constructed of one or morestructural elements which can comprise structural materials, e.g. ameans for conferring rigidity, thermal conductive material, e.g. a meansfor heat transfer to and from a temperature differential generatingmeans, and atomic reflection material, e.g. means for providing adesirable reflection kernel properties. In some embodiment, individualhot and cold layers may be constructed of layered composites of suchmaterials.

Thus, the choice of materials is and composition is widely variable. Insome embodiments, materials suitable for construction of NMSET orrelated device can include titanium, silicon, steel, and/or iron.Titanium is light weight and possesses a hexagonal crystallinestructure. Interfaces of titanium may be created at orthogonal angleswithout crystalline warping and therefore no stress limit. Materialcosts of titanium are high. Silicon is inexpensive and has wellunderstood properties and processes for machining. The crystallinestructure of silicon is diamond cubic. Steel is cheaper than titanium,possesses a cubic crystalline structure, and is highly resistant togaseous intrusion. Iron is cheaper than steel and has a crystalline formwhich makes it suitable for application in NMSET and related devices.

Exemplary Methods of Manufacturing NMSET or Related Device

According to one embodiment as shown in FIG. 20, a method ofmanufacturing an NMSET or related device comprises: (a) providing asuitable substrate 2001 such as, for example, amorphous silicon,crystalline silicon, ceramic, etc., the substrate preferably having athickness of 500 to 1500 microns; however thinner and thicker substratesare possible; (b) depositing a first layer 2002, a mostly sacrificiallayer, preferably an electrical insulator, such as, for example, silicondioxide, the first layer 2002 preferably having a thickness of 200 nm to50 microns, however thinner and thicker layers are possible.Furthermore, depending on the area of the substrate window 2001 a, it isadvantageous for this layer to have a tunable stress level. For example,for a 1 cm² substrate window 2001 a, successful results have beenachieved with SiO_(x)N_(y) at 60 MPa tensile strength; (c) forming apattern of discrete islands in any suitable shape such as, for example,strip, square, circle from the first layer 2002 by photolithography andetching the first layer 2002; (d) depositing a second layer 2003 overthe discrete islands, the second layer 2003 being an electricalconductor such as, for example, Al, Nb or Zn, preferably having athickness of 5 to 200 nm, however, other thicknesses are contemplated;(e) depositing a third layer 2004 over the second layer 2003, the thirdlayer 2004 being an electrical insulator such as, for example, silicondioxide or the same material used in layer 2002, preferably having thesame thickness as the first layer 2002, however, other thicknesses arecontemplated; (f) partially removing the third layer 2004 and the secondlayer 2003 until the first layer 2002 is exposed; (g) depositing afourth layer 2005, the fourth layer 2005 being an electrical insulatorsuch as, for example, silicon dioxide preferably of the same material as2003, the fourth layer 2005 preferably having a thickness of 3 to 15 nm,thinner is better as long as there are few or no gaps in coverage; (h)depositing a fifth layer 2006, the fifth layer being an electricalconductor such as, for example, Pt, Ni or Cu, and preferably having athickness of 5 to 200 nm, however, other thicknesses are contemplated;(i) depositing a sixth layer 2007, such layer being formed to protectthe front side of the substrate while the backside is being worked on.Such layer can be made of, for example, wax, photoresist, or silicondioxide substrate attached to the fifth layer 2006 via thermal releasetape, the sixth layer 2007 preferably having a thickness of 500 to 1500microns, however, other thicknesses are contemplated; (j) formingthrough holes 2001 a in the substrate 2001 by photolithography andetching the substrate 2001, such that at least one discrete island ofthe first layer 2002 is exposed therein, the through holes 2001 a havingany suitable shape such as, for example, hexagons, squares and circles,the through holes 2001 being arranged in any suitable pattern such as,for example, a hexagonal grid, square grid and a polar grid; (k)removing exposed discrete islands by etching until portions of thefourth layer 2005 there above are exposed; (l) removing exposed portionsof the fourth layer 2005 by etching until portions of the fifth layer2006 there above are exposed; (m) removing exposed portions of the fifthlayer 2006 by etching; (n) partially removing the fourth layer 2005 byetching laterally such that the second layer 2003 and the fifth layer2006 overhang the fourth layer 2005 by 2-10 nm; (o) completely removingthe sixth layer 2007 by thermal release, dissolving or etching. Thesecond layer 2003 and the fifth layer 2006 preferably have a differenceof at least 0.1 eV, at least 1 eV, at least 2 eV or at least 3 eV intheir work-functions.

According to another embodiment as shown in FIG. 21, a method ofmanufacturing an NMSET or related device comprises: (a) providing asuitable substrate 2101 such as, for example, amorphous silicon,crystalline silicon, ceramic, etc., the substrate preferably having athickness of 500 to 1500 microns; however thinner and thicker substratesare possible; (b) depositing a first layer 2102, a mostly sacrificiallayer, preferably an electrical insulator such as, for example, silicondioxide, the first layer 2102 preferably having a thickness of 50 nm to1000 nm; however thinner and thicker layers are possible. Furthermore,depending on the area of the substrate window 2101 a, it is advantageousfor this layer to have a tunable stress level. For example, for a 1 cm²substrate window 2101 a, successful results have been achieved withSiO_(x)N_(y) at 60 MPa tensile strength; (c) depositing a second layer2103 over the first layer 2102, the second layer 2103 being anelectrical conductor such as, for example, Al, Nb or Zn and preferablyhaving a thickness of 5 to 150 nm, however, other thicknesses arecontemplated; (d) depositing a third layer 2104 over the second layer2103, the third layer 2104 being an electrical insulator such as, forexample, silicon dioxide and preferably having a thickness of 5 to 100nm, however, other thicknesses are contemplated, and preferably the samematerial as 2102; (e) depositing a fourth layer 2105 over the thirdlayer 2104, the fourth layer 2105 being an electrical conductor such as,for example, Pt, Ni or Cu and preferably having a thickness of 5-150 nm,however, other thicknesses are contemplated; (f) forming holes throughthe second layer 2103, the third layer 2104 and the fourth layer 2105 byphotolithography and etching, the holes having any suitable shape suchas, for example, strips, squares, circles; (g) partially removing thethird layer 2104 by etching laterally such that the second layer 2103and the fourth layer 2105 overhang the third layer 2104; (h) formingthrough holes 2101 a in the substrate 2101 by photolithography andetching the substrate 2101, such that at least one hole through thesecond layer 2103, the third layer 2104 and the fourth layer 2105overlaps with one through hole 2101 a, the through holes 2101 a havingany suitable shape such as, for example, hexagons, squares and circles,the through holes 2101 being arranged in any suitable pattern such as,for example, a hexagonal grid, square grid and a polar grid; (i)removing portions of the first layer 2102 exposed in the through holes2101 a. The second layer 2103 and the fourth layer 2105 preferably havea difference of at least 0.1 eV, at least 1 eV, at least 2 eV or atleast 3 eV in their work-functions.

Exemplary Thermal Transpiration Devices with Vacuum Layer

Though somewhat redundant, FIG. 22 is a side cross-sectional viewillustrating a thermal transpiration device, such as NMSET or relateddevice, shown generally at 2204. The thermal transpiration deviceincludes a cold side membrane 2202 and a hot side membrane 2201, with athermal insulator 2200 provided in between. The thermal insulator 2200may be formed of a vacuum, which can be achieved, for example, via theVenturi effect. The thermal transpiration device 2204 includes athickness 2203 defined by the cold side membrane 2202, the thermalinsulator 2200 and the hot side membrane 2201.

FIG. 23 is a side cross-sectional view illustrating the operation of athermal transpiration device, shown generally at 2309. The device 2309includes a hotter layer 2301, a colder layer 2302, with a thermalinsulator 2300 provided there between. Apertures 2308 are formed in thedevice 2309 in a manner as previously described. The thermaltranspiration device 2309 includes a thickness 2303 defined by thecolder layer 2302, the thermal insulator 2300 and the hotter layer 2301.The thermal insulator 2300 can be formed of a vacuum, which can beachieved, for example, via the Venturi effect.

Colder gas particles 2304, which have a mean free path (average distancetraveled before hitting another particle) shown by radius 2305, enterthe aperture 2308, or the edge thereof, and collide with otherparticles, thus exchanging energy. Hotter gas particles 2306, which havea mean free path shown by radius 2307, collide into the hotter layer2301, thus gaining energy in the process and imparting a positivemomentum force. The colder gas particles 2304 reduce the temperature ofthe hotter gas particles 2306, which collide back into the hotter layer2301, thus gaining energy and imparting a positive momentum force andincreased pressure on the hot layer 2301.

FIGS. 24 and 25 are respective side and top cross-sectional views of athermal transpiration device, shown generally at 2414, with one extendedlayer having angled walls. The device 2414 includes a hotter layer 2401and a colder layer 2402, with a thermal insulator 2400 provided therebetween. The thermal insulator 2400 can be formed as a vacuum, which canbe achieved, for example, via the Venturi effect. The total thickness ofthe device 2414 is indicated by reference number 2403, and is defined bythe colder layer 2402, the thermal insulator 2400 and the hotter layer2401.

Apertures 2408 are provided in the device 2414, forming angled walls2415 in the hotter layer 2401, in a manner as previously described. Theapertures 2408, and/or edges thereof, aid in defining a hotter surface2409, a colder surface 2410, an active area 2411 generally where thermaltranspiration occurs, and a support area 2412. As shown in FIG. 24, theangle 2413 of the hotter surface 2409 is less than 90-degrees in orderto form the angled walls 2415.

While FIGS. 24 and 25 illustrate the extended layer having angled wallsas being the hotter layer 2401, one skilled in the art will appreciatethat the colder layer 2402 could be implemented as the extended layerhaving angled walls as an acceptable alternative.

FIGS. 26 and 27 are respective side and top cross-sectional views of athermal transpiration device, shown generally at 2615, with one extendedlayer having wet or dry etched walls. The device 2615 includes a hotterlayer 2601, a colder layer 2602, with a thermal insulator 2600 providedthere between. The thermal insulator 2600 can be formed as a vacuum,which can be achieved, for example, via the Venturi effect. The totalthickness of the device 2615 is indicated by reference number 2603, andis defined by the colder layer 2602, the thermal insulator 2600 and thehotter layer 2601.

Apertures 2608 are provided in the device 2615, and forming wet or dryetched walls 2614 in the hotter layer 2601 having a generally parabolicshape, in a manner as previously described. The apertures 2608, and/oredges thereof, aid in defining a hotter surface 2609, a colder surface2610, an active area 2611 generally where thermal transpiration occurs,a support area 2612 and wet or dry etched surfaces 2614.

Reference number 2605 indicates the mean free path radius of colder gasparticles 2604. Reference number 2607 indicates the mean free pathradius (the average distance traveled before hitting other particles) ofhotter gas particles 2606. The colder gas particles 2604, enter theaperture 2608, or the edge thereof, and collide with other particles,thus exchanging energy. The hotter gas particles 2606 collide into thehotter layer 2601 at the outer edge thereof or at the wet-etched surface2614, thus gaining energy in the process and imparting a positivemomentum force. The colder gas particles 2604 reduce the temperature ofthe hotter gas particles 2606, which collide back into the hotter layer2601 thus gaining energy and imparting a positive momentum force andincreased pressure on the hot layer 2601.

While FIGS. 26 and 27 illustrate the extended layer having wet-etchedwalls as being the hotter layer 2601; one skilled in the art willappreciate that the colder layer 2602 could be implemented as theextended layer having angled walls as an acceptable alternative.

FIG. 28 is a side cross-sectional view of a thermal transpirationdevice, shown generally at 2816, with two extended layers having angledwalls. The device 2816 includes a hotter layer 2801 and a colder layer2802, with a thermal insulator 2800 provided there between. The thermalinsulator 2800 can be formed as a vacuum, which can be achieved, forexample, via the Venturi effect. The device 2816 has a total thickness2803, defined by the colder layer 2802, the thermal insulator 2800 andthe hotter layer 2801.

Apertures 2808 are provided in the device 2816, forming angled walls2817 and 2818 in the hotter 2801 and colder 2802 layers, respectively,in a manner as previously described. The apertures 2808, and/or edgesthereof, aid in defining a hotter surface 2809, a colder surface 2810,an active area 2811 generally where thermal transpiration occurs, asupport area 2812 for the hotter layer 2801, and a support area 2815 forthe colder layer 2802. As shown in FIG. 28, the angle 2819 of both thehotter 2809 and colder 2810 surfaces are less than 90-degrees in orderto form the angled walls 2818 and 2817, respectively. While the angles2819 of the hotter 2809 and colder 2810 are shown in FIG. 28 as beingapproximately the same angle, the hotter 2809 and colder 2810 surfacesmay be angled at different angles as an acceptable alternative dependingon the embodiment.

In an ideal thermal transpiration device, the total thickness of theactive area of the device designed to operate in atmosphere should beless than 500 nm. For optimization purposes, the thickness between thehot and cold surfaces should be no greater than 100 nm. Such smallthicknesses make the device extremely fragile and difficult to workwith. If, for example, the device layers, or membranes, are made thickerin order to provide the required thickness for the stability andstrength of the device, its overall thickness would increase to a pointthat it exceeds the ideal thickness, as discussed above.

FIG. 29 is a cross-sectional view of the beginning construction of oneembodiment of a thermal transpiration device, shown generally at inaccordance with the present disclosure, which allows the thickness of athermal transpiration device to be made thicker to enhance it durabilityand strength, while at the same time maintaining the thickness of thedevice in its critical area to within an ideal thickness range.

As shown in FIG. 29, the construction of the device is as follows.First, a silicon substrate layer 2916 is provided. A first metal layer2917 of, for example, approximately 40 nm of aluminum, is deposited onthe substrate 2916. The deposition process may be evaporation, but otherdeposition methods may be used, such as, for example, sputtering, metalorganic vapor deposition, etc. Hence, the first metal layer 2917 may be40 nm of evaporated aluminum.

A dielectric layer 2918 is deposited on top of the first metal layer2917. The dielectric layer 2918 must be low stress and may be formed ofa plastic or inorganic non-electrically conducting film material. Thefilm (i.e., dielectric layer 2918) may be, in particular, low-stress(e.g., 60 MPa) plasma enhanced chemical vapor deposition oxynitride thatis 2 microns thick. Other thicknesses are also contemplated.

An adhesion promoter layer 2919 may be deposited on dielectric layer2918 to promote adhesion to the dielectric and or to act as an enhancedmasking layer. Such material may be a chemical monolayer, such as HMDS,a thin film of organic resist, or a metal, in particular, 6 nm ofchromium. The adhesion promoter layer 2919 may not be necessary oncertain combinations of thin films and etching methods or etchingchemicals.

The device is then etched, as is conventionally known, using a mask 2920of approximately 1.3 microns SPR-3012, for example, with an unmaskedarea 2921. Etching may be achieved by depositing the photoresist layer,or mask, 2920 over the adhesion promoter layer 2919, as is known to doby one of ordinary skill in the art. Such a photoresist is preferablyShipley SPR-3012; however, other photoresists may be utilized. Thephotoresist layer 2920 may then be exposed through a conventional maskto develop unmasked areas 2921. Exposure can be made, for example, usingan appropriate wavelength of light. Contact lithography may also be usedas would be understood by one of ordinary skill in the art. Onceexposed, the photoresist layer 2920 may be developed in a solutionappropriate for that purpose to form the unmasked areas 2921. Such asolution may be, for example, 0.26M tetramethylamonium hydroxide forSPR-3012 for approximately 60 seconds.

As shown in FIG. 30, the device is etched at the unmasked areas 2921(see FIG. 29) to form etched areas 3022. The etched areas 3022 areformed by etching into the adhesion promoter layer 2919 and thedielectric layer 2918 until portions of the first metal layer 2917 areexposed. The photoresist layer 2920 (see FIG. 29) is then removed. Theadhesion promoter layer 2919 may be etched using a wet etch, such as,for example, a chromium etch 1020 from Transene, until the siliconsubstrate 2916 is exposed. The dielectric layer 2918 may be etched, forexample, with a chemical that will not etch the first metal layer 2917.In the case of oxynitride on aluminum, the aqueous acid solution SiloxVapox II from Transene can be used. Other wet chemistries may also beused, or a dry plasma etch.

FIG. 31 is a side cross-sectional view showing further etching of thethermal transpiration device shown in FIGS. 29-30. Reference number 2916is the silicon substrate, reference number 2917 is the first metallayer, reference number 2918 is the dielectric layer, and referencenumber 2919 is the adhesive promoter layer. In FIG. 31, the device,namely, the etched area 3022 (see FIG. 30), has been further etched toprovide an etched area 3122 and under cut area 3123. To form the etchedarea 3122, the first metal later 2917 is etched, and then portions ofthe substrate 2916 are etched. One method of forming the undercut areas3123, portions of the substrate 2916 which are underneath the firstmetal layer 2917 are isotropically etched.

The first metal layer 2917 may be etched with either wet or dry etching.In the case of aluminum, for example, an aluminum etch in a reactive ionetcher with chlorine and argon at low pressure may be used to etch thefirst metal layer 2917. An example of an etch for 40 nm of aluminum is50 sccm BCl3, 20 sccm Cl2, 10 mTorr, with 300 W RF power.

A wet or vapor etch can be used to etch the substrate 2916, as long asthe chemistry does not etch the first metal layer 2917, the dielectriclayer 2918 or the second metal layer 2919. In the case of a siliconsubstrate with aluminum and oxynitride, the silicon may be etched, forexample, with the gas XeF2. The substrate 2916 may also be treated toremove boron. One exemplary method of such a treatment is to use afluorine based reactive ion plasma under the conditions of 35 sccm CF4,20 mTorr, and 300 W RF power.

FIG. 32 is a cross-sectional view showing further formation of thethermal transpiration device shown in FIGS. 29-31. A thin layer 3224 ofsilicon dioxide or another electrical insulator is provided over thedevice. The silicon dioxide layer 3224 can be, for example,approximately 2-10 nm thick. Thinner is generally better as long asthere are few or no gaps in coverage, especially near the first metallayer 2917. The layer 3224 of silicon dioxide is provided to controltunneling thickness. The layer 3224 can be added by evaporation, orother known techniques. For example, other methods, such as sputtering,plasma enhanced chemical vapor deposition, atomic layer deposition,etc., may be used as well, along with other materials. A second metallayer 3225 is provided over the silicon dioxide layer 3224. The secondmetal layer 3225 may be a layer of metal, such as nickel or copper, andmay be approximately 40 nm thick. The second metal layer 3225 may beformed by evaporation, but other methods may be used as well, such as,for example, sputtering or ion assisted deposition.

The substrate 2916 is then mounted to a carrier substrate (not shown)with the thin film stack facing the carrier. The mount material couldbe, for example, a double-sided tape, such as Revalpha thermal releasetape. However, other tapes and materials, such as, for example, wax orphotoresist, may be used as well.

The remaining silicon substrate 2916 is then removed with, for example,an XeF2 vapor etch. The small portions of the silicon dioxide layer 3224and the second metal layer 3225 formed in the etched portion of thesubstrate 2916 are removed with the substrate 2916. Wet chemistry mayalso be used to remove the substrate 2916, as long as it does not etchthe first and second metal layers 2917 and 3225. What is left, as shownin FIG. 33, are the islands 3127 formed by the first metal layer 2917,the dielectric layer 2918, the adhesion promoter layer 2919, the thermotunneling layer 3224, and the second metal layer 3225. The device isthen sonicated to remove any Nickel plugs. In the case of Revalphathermal release tape, for example, the carrier substrate can be placedon a hotplate of sufficient temperature to aid in removing the device.

Fault Tolerant Control System for Distributed Micro-Thrusters

In order to drive an object using distributed thrusters in a particulardirection and or at a desired speed, a control system is needed. Thecontrol system is used to selectively activate and or adjust powerlevels to a distributed thruster or plurality of distributed thrustersto provide the desired force in the desired direction.

In accordance with the present control system, a control system forcontrolling the operation of distributed thrusters may be constructed asa grid of elements (each containing one or more thrusters) fed by atleast a redundant two dimensional network of power distribution wiring.The distribution network is constructed as a plurality of loopscomprised of horizontal and vertical lines or wires that are coupled toa plurality of horizontal rows and vertical columns of thrusters.

According to one embodiment of the present control system, each row andcolumn loop meet or intersect in at least four locations, butalternating topologies may be designed to balance redundancy, number ofloops, and the granularity of addressing. Alternate topologies may havea different number of crossings.

At least one power source may be supplied for each element in the gridor for a plurality of elements. One element may contain a plurality ofthrusters. One terminal of the power source is connected to a horizontalline, and the other terminal of the power source is connected to avertical line. This connection permits an element or group of elementsto be addressed by connecting the terminals of a power source to theappropriate row and column.

In accordance with the general operation of the distributed thrusterssuch as NMSET, an electrical circuit is used to activate distributedthrusters by supplying and or regulating the amount of heat to thedistributed thruster. An electrical circuit is formed by a loopcomprised of the horizontal and vertical lines. Both ends of a givenloop are driven at the same electrical potential. This means that asingle cut anywhere in a given loop (as a result, for example, fromdamage to the array surface) will minimize a cascading loss offunctionality. The heating or cooling caused by electrical circuit maybe implemented by way of a heat pump, such as one driven by the Peltiereffect using a Peltier slab. In this instance, the wiring are on eitherside of the distributed thrusters, and in a resistance embodimentexplained below, they may be only on the hot side. In furtherembodiments of distributed thrusters, other methods of powering thedistributed thrusters can be used.

FIG. 34 is a top view of one embodiment of a control system 3400 for anarray 3401 of distributed thrusters 3402 in accordance with the controlsystem. As can be seen in FIG. 34, in the array 3401, a plurality ofdistributed thrusters 3402 are arranged in a grid-like manner inparallel horizontal rows and parallel vertical columns.

At least one power supply 3406 provides power to selected distributedthrusters 3402 using a first plurality of power lines 3404 and a secondplurality of powers lines 3405 which are coupled to the distributedthrusters in each of the horizontal rows and in each of the verticalcolumns, respectively. When one of the power lines 3404 is selectedalong with one of the power lines 3405, an electrical circuit iscompleted and at least one of the distributed thrusters is activated bythe methods the distributed thrusters convert energy into thrust. Acontrol unit 3403 controls the activation and or power levels of theselected power lines 3404 and 3405 for the desired thruster or group ofthrusters.

As used in the present control system, the power supply 3406 may be abattery and the control unit 3403 may be a central processing unit.Further, thruster 3402 may comprise a plurality of thruster devices.

A NMSET device may comprise an apparatus operable to propel a gas wherethe apparatus comprises at least a first layer and a second layerarranged in a stack and means for heating and/or cooling the first andsecond layers to form a hot layer and a cold layer wherein the coldlayer has a lower temperature than the hot layer, and at least onethrough hole in the stack. A surface of each hot layer is exposed in aninterior of the through hole, a surface of each cold layer is exposed inthe interior of the through hole, and an entire length of the activearea of the through hole is up to 10 times of a mean free path of a gasin which the apparatus is immersed and/or is not greater than 1500 nm,as explained above.

In a given NMSET device at least one through hole may have a straightgeometry, a sawtooth geometry, a triangular geometry, a parabolicgeometry, or any geometry that may be determined to be beneficial forthe NMSET device, as explained above.

FIG. 35 illustrates power lines 3504 and 3505 that meet at area 3506 toactivate the distributed thruster's adjacent area 3506. The control unit3503 activates the distributed thruster's adjacent area 3506 by causingthe power supply 3506 to provide electricity to power lines 3504 and3505.

FIG. 36 illustrates a fault condition where there is an open circuit inpower line 3605. As shown in FIG. 36, power line 3605 is associated witha vertical column of thrusters that are associated with the area aroundpoints 3608. Because there is an open circuit 3607 in power line 3605,the thrusters associated with the area around points 3608 cannot beactivated due to this fault condition.

In one embodiment of the control system, in order to achieve redundancyand avoid system failure when a fault condition occurs in a power line,redundant path connections are provided as illustrated in FIG. 37. Powerlines 3701 are coupled to the horizontal rows of thrusters and thatpower lines 3702 are coupled to the vertical columns of thrusters. Thus,a redundant path is provided to point 3706 in the event that a fault3707 occurs in line 3705 as shown in FIG. 37. Redundancy is provided bypower lines 3705 and 3704 wherein the control unit 3700 rerouteselectricity from the first to the second connection point of power line3707 or the power line is internally looped to activate the thrustersnear point 3706. In another embodiment of the present control system, afault detection device 3708 is provided to detect a fault condition inany one of the power lines as shown in FIG. 37. The fault detectiondevice 3708 is coupled to the power supply 3703 and control unit 3700and which controls activation of an appropriate power line to compensatefor, reroute, report and or replace the power line in which the faultcondition is present.

A capacitor bank voltage sensing technique may be used to detect afault. By designing the capacitor bank to not discharge completely in asingle pulse, and measuring the voltage charge before and after a powerpulse has been sent to a thruster element or a group of thrusterelements, it is possible to determine the power consumed by the thrusteror group of thrusters and compare this to the expected power. If thedrop is significantly smaller than expected, this is a sign of an opencircuit; a significantly large drop indicates a short.

In-line current sensing may also be used to detect a fault. A shuntresistor may be placed in series with the power distribution lines inorder to measure the instantaneous current being drawn by the array. Ifthe current is usually low, some cells may be open. If the current isexcessively high, there is a short. The primary disadvantage of thismethod is that it increases the series resistance between the powersupply and the thrusters by a small (but nonzero) amount.

The significant advantage of this method over sensing the capacitorvoltage after a pulse is that it is possible to design a system fastenough (most likely at a few MHz level sampling rate) to respond in realtime to a short circuit and abort the pulse before enough energy hasbeen released to cause serious damage to adjacent thrusters from arcing,or to the power supply from rapid discharge and consequentlyoverheating. This system may also be applied to a distributed thrustersoperated in the continuous-duty mode.

Once a portion of the distributed thrusters has been declared faulty byany of the above methods, or another method as recognized by one ofordinary skill in the art, corrective action must be taken to minimizeloss of thrust and or prevent cascading failures.

When performing timing analysis of pulsed distributed thrusters duringthe design phase, it is prudent to allow more than the minimum requiredcool-down time between successive pulses to any section of thrusters. Ifthis is done, the overall thrust may be maintained by removing thedamaged thrusters or section of thrusters from the firing sequence andoperating the remaining undamaged thrusters or sections at a slightlyincreased duty cycle.

An increase in duty cycle can only compensate for a maximum amount ofdamage to the system. If this threshold is exceeded, a reduction inavailable thrust is unavoidable; an array's control system can bedesigned to compensate for loss of thrust capacity on one side of acraft or other application using the distributed thruster by slightlyreducing the thrust on the corresponding opposite panel to maintain alevel trim.

FIG. 38 is a top view of another embodiment of an exemplary controlsystem, particularly useful for larger distributed thrusters systemsand/or applications that can use a less granular control. Thisembodiment may be advantageous due to the decrease in the number ofpower and/or control lines, and/or the decrease in the requiredcomputing power, than what would normally be required for more granularcontrol. The exemplary control system is showing an array of powersupply lines 3801 and 3802 and sub power line 3810 that are used toactivate sections of a group of distributed thrusters 3803, 3804, 3805,and 3806 (shown in dotted line and which may further include a pluralityof individual thrusters at the power line intersections). For example,the control unit 3800 may connect the power supply 3803 to anappropriate power line of power supply lines 3801 and an appropriatepower line of power supply lines 3802 in order to cause electricity toflow in the corresponding sub power lines 3810 at and around thecorresponding thruster or regions of thrusters in 3803, 3804, 3805,3806. Additionally, the control unit 3800 can be designed to activatethrusters region 3803 and thrusters region 3805 or 3804 or 3806simultaneously, sequentially, or in a desired pattern or for a desiredeffect by causing electricity to flow in the appropriate power lines ofpower supply lines 3801, 3802 and sub power lines 3810 and through theinclusion of an additional microprocessor at the intersections of subpower lines with the power lines, and using a digital signal tocommunicate with those microprocessors.

FIG. 39 is a top view of a further embodiment similar to that shown inFIG. 38 of an exemplary control system. FIG. 39 illustrates a pluralityof power supply lines 3901 and 3902 and a plurality of sub-power supplylines 3910 that form a grid structure as shown. The control unit 3900may connect the power supply 3911 to an appropriate power line of powersupply lines 3901 and an appropriate power line of power supply lines3902 in order to cause electricity to flow in the sub-power lines 3910at and around the corresponding thruster or regions of thrusters 3903.Furthermore, as discussed with FIG. 38, the control unit 3900 mayactivate any of distributed thrusters 3903, 3904, 3905, 3906, 3907,3908, and 3909 in a group or individually.

FIGS. 40a, 40b and 40c shows an enlarged illustration of the embodimentof the control system shown in FIG. 34. Power lines 4001 and 4002 areused to address the thruster regions that operate on temperaturegradients 4006 around addressed point 4003. When the thrusters aroundpoint 4003 are addressed due to the flow of electrical current throughpower lines 4001 and 4002, point 4003 heats up with area 4004 being theprimary area affected and area 4005 being the secondary area affected.

Because it may be undesirable for the heating of one point to causeheating of adjacent points, another exemplary embodiment is illustratedin FIGS. 41a and 41b , which shows the inclusion of a heat barrier 4117,which may be in the form of a conductive pad, an insulator, a gap, orany other form of heat barrier as recognized by one of ordinary skill inthe art. The heat barrier 4117 has the effect of changing the heatconductivity and isolating the conductive areas. The heat barrier 4117is shown as a perimeter around the thruster regions 4108 that areadjacent a junction 4106 of power lines 4105 and 4104, however the heatbarrier 4117 may be configured differently based on a different desiredeffect. By energizing power lines 4105 and 4104 the thruster regions4108 adjacent junction 4106 are activated and the heat barrier 4117prevents other thruster regions outside of the shaded box area shown as4119 from being inadvertently activated.

FIGS. 42a, 42b and 42c show the power lines or conductive structures ofanother embodiment of the control system. FIG. 42a shows a top layergrid structure 4202 of conductive lines to be used for activatingthruster regions, where power supply line 4200 is designed to beconnected to a power supply and a plurality of branch lines 4201 aredesigned to be positioned in proximity to a plurality of thrusterregions.

FIG. 42b illustrates an optimized middle layer showing insulators 4202and resistors, temperature gradient generating device or other means ofactivating thruster regions 4203 to be used in between the gridstructure shown in FIG. 42a and further grid structure that willintersect the branch lines 4201 in FIG. 42a at the thruster regions4203.

FIG. 42c illustrates the combination of FIGS. 42a and 42b , where thetop layer of FIG. 42a is placed over the middle layer of FIG. 42b . FIG.42c shows power supply line 4200 and branch lines 4201 overlaid onto thethermo-resistive heating junctions formed by resistors 4203 ortemperature gradient generating device or other means of activatingthruster regions and insulators 4202 as in an embodiment of the controlsystem, to control a plurality of target points from a single power lineintersection point.

Exemplary Resistive Temperature Gradient Formation

Reference is made to the section entitled “Principles of Operation” andsubsection “Temperature Differential”, above, incorporated here byreference. FIG. 43 is schematic diagram of a device that can be used tocreate a temperature gradient in accordance with the present disclosure.In this section, the heat pump or thermal gradient device may be, but isnot limited to driving a NMSET device. The device includes a colderlayer 4301 of an electrically conductive material having a top surface4302 and a bottom surface 4305. A top surface 4306 of a hotter layer4304 is closely proximate to and may be attached to bottom surface 4305of colder layer 4301 directly or through a thermally and/or electricallyinsulating intermediate material depending on implementation.

One terminal of power supply 4307 is connected to top surface 4302 ofthe colder layer 4301 and the other terminal of power supply 4307 isconnected to one side of switch 4308. The other side of switch 4308 isconnected to bottom surface 4303 of the hotter layer 4304. The hotterlayer 4304 is made of or is a structure with sub-layers that include alayer of a resistive material that heats up through resistive or Jouleheating when electrical current passes through it. In embodiments withsub-layers, one might be an insulating material with reduced thicknessnear the locations a thermal gradient is to be produced, and ametallization layer that is configured to heat at a greater rate at thethermal gradient locations.

The colder layer 4301 might be of a material less subject to Jouleheating in the operative locations. The difference in resistive, Jouleheating characteristics can be accomplished through selection ofmaterials, configuration (e.g., the hotter layer being thinner at thesites where heat is to be generated when compared to an opposinglocation of the colder layer so that the electron density in the hotterlayer promotes Joule heating at a greater extent that the colder layer)or other factors that permit one layer to heat up to a greater extent orfaster than an adjacent layer, or combinations thereof of thesecharacteristics, depending on a particular embodiment. For instance, thehotter layer can be made up of surface wires that thin or become morenarrow or otherwise have smaller in cross-section at sites where heatingis desired, e.g., at a NMSET structure or groups of NMSET structures,such that the charge carrier density/resistance is greater at thosesites, and Joule heating is more apparent. The colder layer can be athicker, less resistive material having a broader area (e.g., cover theentire surface of the hotter layer) to reduce carrier density. Whateverthe mechanism, the current in one layer promotes Joule heating, and inthe other layer does not, at least not to the same extent of Jouleheating in the one layer.

Further, the mechanism for passing current from one layer to the othercan follow any suitable method or mechanism, such as quantum tunneling,semiconductor conduction were the colder and hotter layers are P-typeand N-type semiconductors forming a PN junction, with electrode formedthereon on opposing surfaces, transistors connected to address line,similar to the read/write and address lines of memory devices, thatpermit an adjacent electrode to heat on one surface, with the switchbeing much like the structure of an addressable memory site or pixel,but with the memory site or pixel structure being replaced with anelectrode that thermally heats, or nearly any other type of structurethat will selectively address thermal gradient devices or clusters ofsuch devices.

Alternatively or additionally, the hotter layer can have an input sideand an output side in the same layer, wherein current passes throughfrom one side to the other, resistively heating the hotter layer. Thisembodiment can produce heat at selected sites, and less so elsewhere,when the hotter surface is not entirely covered by an electricallyconductive material, but rather has conductive lines, wherein the lineshave characteristics that permit heating at selected sites, such asNMSET structures of groupings. That is, the lines can be large enough iscross-section to not heat, but at selected sites have a reducedcross-section to selectively heat upon application of current.

In the embodiment of FIG. 43, electrical current passes from the toplayer 4301 to the bottom layer 4304. As shown in FIG. 43, switch 4308 isin an open condition. Thus, no current flows through layers 4301 and4304. Accordingly, there is no temperature gradient or difference intemperature between surface 4302 and surface 4303.

FIG. 44 showing the state where switch 4406 is closed. Thus, currentfrom power supply 4407 flows through layers 4401 and 4402. As result ofthe current flow, layer 4402 begins to heat because of its resistivecharacteristics, thus causing layer 4401 to heat as well. The heating oflayer 4402 causes a temperature gradient 4405 to be created between toplayer 4403 and bottom layer 4404. When switch 4406 is opened, current nolonger flows through layers 4401 and 4402. Thus, temperature gradient4405 begins to diminish eventually to zero difference in temperaturebetween surfaces 4403 and 4404.

FIG. 45 plots of the temperature increase of surface 4404 as currentbegins to flow when switch 4406 is closed. Temperature is plotted alongthe y-axis and time is plotted along the x-axis. Note that thetemperature of surface 4404 in FIG. 45 rapidly rises as indicated byplot 4501 to an equilibrium temperature 4504. The switch 4406 in FIG. 44is then opened and current no longer flows, the temperature will beginto drop.

The temperature of surface 4403 when switch 4406 is closed follows asimilar but delayed pattern 4507 as the heat from layer 4402 begins tomigrate toward surface 4403 through layer 4401 as indicated by plot4502. The temperature of surface 4403 continues to rise even slightlyafter the switch 4406 in FIG. 44 has been opened, to its equilibriumtemperature 4505. Reference number 4506 in FIG. 45 indicates the lengthof time that switch 4406 remained closed. If the length of time 4506 theswitch 4406 remains closed exceeds the time it takes to reachequilibrium temperature 4504, than the temperature of surface 4403 willcontinue to rise, until the temperature gradient 4503 vanishes.

Thus, the temperature gradient between temperature 4504 of surface 4404and the temperature 4505 of surface 4403 at a given time is representedin FIG. 45 as temperature gradient 4503.

As FIG. 45 illustrates, it takes a finite amount of time for thetemperatures of surfaces 4403 and 4404 to return to their ambient stateafter current stops flowing through layers 4301 and 4304. The residualheat can cause problems if adjacent temperature gradient devices are inclose proximity.

FIG. 46 is a top cross-sectional view of a plurality of distributedthruster devices such as one operated by temperature gradient devices4603 arranged in horizontal and vertical rows in accordance with anotherexemplary embodiment. Current flow is supplied to each device by aplurality of power lines 4601 and 4602 from a power and control unit4300 in a matrix type manner. The control unit may be formed of aprocessor, particularly a programmable processor that can selectivelyactuate particular sites, as explained above with respect to controlelectronics at the active sites when the power lines operate likeread/write and address lines to control adjacent control electronics atthe active site, or simply by adding current to horizontal and verticalpower lines such that at cross points enough current is present tocreate a temperature gradient. A source of electrical energy may beformed of a battery, or any other source of carriers, whether AC or DC,depending on implementation. Also, the section entitled “Fault TolerantControl System”, above, is incorporated herein

With reference again to FIG. 46, if an adjacent temperature gradientdevice 4603 is activated before the first temperature gradient device4603 is allowed to fully cool, the temperature gradient of the newlyactivated device may not be the expected gradient. Depending on theapplication, this may not be optimal. Such a condition is illustrated inFIG. 47 (and similarly in FIGS. 40a, 40b and 40c , for instance) where atemperature gradient device 4703 is activated by power lines 4704 and4705. As shown in FIG. 47, the generated heat radiates to a primary area4701 and further to a secondary area 4702. Note that the radiated areaencroaches upon other adjacent temperature gradient devices and couldcause those devices not to produce the proper temperature gradient whenthey are activated. This potential problem can be mitigated or resolvedby the selective activation of thermal gradient devices.

For example, the control unit 4600 shown in FIG. 46 avoids activation ofthose temperature gradient devices that are adjacent previouslyactivated temperature gradient devices for a predetermined period oftime. Doing so allows the previously activated temperature gradientdevice to fully cool, or at least cool to a satisfactory temperature, sothat no residual heat interferes with the operation of adjacenttemperature gradient devices. Further, the temperature gradient devicescan be selectively addressed, either individually or in clusters, byread and address lines in a manner similar to the manner in which pixelson a digital display or memory sites in a memory array are addressed andcontrolled.

FIG. 48 illustrates one embodiment of an activation sequence oftemperature gradient devices in an array of temperature gradient devicesin accordance with this embodiment. Reference number 4801 represents atemperature gradient device in an array of such devices as illustratedin FIG. 46. Reference number 4802 represents an adjacent temperaturegradient device, or an adjacent array of such devices. The patternrepeats as indicated by reference numbers 4803-4816 for a total of 16temperature gradient devices, or arrays of such devices as illustrated,though of course in most embodiments involving NMSET devices there wouldbe more.

Using FIG. 48, one of ordinary skill in the art will readily understandthat an activation sequence for individual or sets of temperaturegradient devices can be determined which avoids or mitigates thermalinterference from a previously activated adjacent device. This is sobecause enough time has elapsed for the previously activated adjacentdevice to sufficiently cool. For example, temperature gradient devicepairs (4801, 4809), (4803, 4811), (4805, 4813) and (4807, 4815) may beactivated followed by pairs (4802, 4810), (4804, 4812), (4806, 4814) and(4808, 4816) without significant causing thermal interference to anypreviously activated adjacent devices. Other activation sequences willbecome known to those skilled in the art from a review of FIG. 48.

As can be seen, the disclosed embodiments can have many applications forcreating and maintaining thermal gradients. In particular, though notlimited thereto, the thermal gradient structures can be in heat pumps todrive distributed thrusters, and even more particularly distributedthrusters driven by NMSET of many forms and variations disclosedelsewhere herein.

FIG. 49 is a top view of one embodiment of an air vehicle 4900 with aplurality of mounts 4901 for thrust generating structures in accordancewith the present invention. In accordance with an exemplary embodiment,each of the plurality of mounts 4901 provides a physical means to attacha thrust generating structure 5002 (see FIG. 50) to a body 4903 of anair vehicle 4900. The plurality of mounts 4901 also provides a means tocontrol the movement and direction of the air vehicle 4900, and as ahosting apparatus or device for a source of power to the air vehicle4900, which is received from the thrust generating structures 5002 (FIG.50). It can be appreciated that each of the plurality of mounts 4901 isconfigured to receive at least one thrust generating structure 5002. Theplurality of mounts 4901 can be attached or fixed to the body 4903 ofthe air vehicle 4900 in pairs or any other desired configuration. Thesource of power to the thrust generating structures may be supplied bythe air vehicle itself.

In accordance with an exemplary embodiment, each of the plurality ofmounts 4901 may include a support or bracket 4904, which attaches themount 4901 to the body of the air vehicle 4903. As shown in FIG. 49,each of the mounts 4901 can be attached in pairs to the air vehicle4900.

FIG. 50 is a top view of an air vehicle 5000 with a plurality of thrustgenerating structures 5002 attached to the mounts 4901 illustrated inFIG. 49. As shown in FIG. 50, each of the plurality of mounts 4901 has athrust generating structure 5002 attached at a distal end thereof. Ofcourse, the thrust generating structure can be attached at any point, aslong as it is structurally sound. It can be appreciated that the thrustgenerating structures 5002 are preferably formed of distributedthrusters. This configuration allows the air vehicle 5000 to becontrolled as a quad copter.

FIG. 51 is a top view of an air vehicle 5100 with attached structures5102 containing at least one nest (or housing) 5103, which is configuredto nest or house a thrust generating module 5104 in accordance with thepresent invention. In accordance with an alternative embodiment, the airvehicle 5100 includes one or more nest or housings, each of which isconfigured to receive a thrust generating module 5104 formed ofdistributed thrusters. In one form, the distributed thrusters can beNMSET elements. Each of the structures 5102 includes a nest 5103, whichreceives at least one thrust generating module 5104. In accordance withan exemplary embodiment, each of the structures 5102 is preferablyrectangular in shape, however, other configurations including round,oval, and/or winged shaped can be implemented without departing from thepresent invention. As shown in FIG. 51, one end of each the structures5102 is attached to the body 5105 of the air vehicle 5100. Thestructures 5102 extend outward having a nest 5103 therein. Each of thenests 5103 is configured to receive at least one thrust generatingmodule 5104.

FIG. 52 is a top view of an air vehicle 5200 having a plurality ofattached structures 5202, wherein each of the plurality of structures5202 contains multiple (or a plurality) nests 5203. As shown in FIG. 52,each of the structures 5202 has a plurality of nests 5203, which areconfigured to receive at least one thrust generating module 5204.

FIG. 53 is a top view of a further embodiment of a structure 5300containing a nest for a thrust generating module in accordance with thepresent disclosure. As shown in FIG. 53, the structure 5300 includes aretainer plate 5305 having a main cavity 5306 therein, which isconfigured to receive a thrust generating module housing 5307. Thethrust generating module housing 5307 receives a thrust generatingassembly 5308. In addition, the structure 5300 also preferably includesa control and power connector 5309.

FIG. 54 is a side exploded view of a structure 5300 containing a nestfor a thrust generating module. As shown in FIG. 54, the structure 5300includes a housing 5303, which is configured to receive at least onethrust generating module. The housing 5303 has a main cavity 5306therein, which is configured to receive the thrust generating modulefrom an underside thereof. The housing 5303 includes a top opening (oraperture) 5311 on an upper surface (or upper portion) and a recessedopening 5312 on a lower surface (or lower portion) thereof. The housing5303 also includes a control and power connector 5309.

The recessed opening 5312 is configured to receive the retainer plate5305 upon insertion of the thrust generating module 5302 into the cavity5306 of the housing 5303. As shown in FIG. 54, the retainer plate 5305has an aperture (or bottom opening) 5313 therein. The thrust generatingmodule includes a thrust generating module housing 5307, and a thrustgenerating assembly 5308. On an upper surface thereof, the retainerplate 5305 includes a recess (or control and power receiver) 5310, whichis configured to receive the control and power controller 5309 uponassembly of the structure 5300.

FIG. 55 is a side exploded view of a structure 5500 containing a nest5501 for a thrust generating module 5502 that is mounted flush to thesurface of the structure 5500. As shown in FIG. 55, the structure 5500includes a housing 5503 having one or more nests, which are configuredto receive at least on thrust generating modules 5502. The housing 5503has a main cavity 5506 therein, which is configured to receive thethrust generating module 5502 from an underside thereof. The housing5503 includes a top opening (or aperture) 5511 on an upper surface (orportion) and a recessed opening 5512 on a lower surface (or portion)thereof. The housing 5503 also includes a control and power connector5509. The recessed opening 5512 is configured to receive the retainerplate 5505 upon insertion of the thrust generating module 5502. Theretainer plate 5505 has a bottom opening 5513 therein. The thrustgenerating module 5502 includes a thrust generating module housing 5507and a thrust generating assembly 5508. On an upper surface thereof, theretainer plate 5505 includes a recess (or control and power receiver)5510, which is configured to receive the control and power controller5509 upon assembly of the structure 5500.

FIG. 56 is a top view of a thrust generating module 5600 with one ormore pressure sensors 5614. As shown in FIG. 56, the thrust generatingmodule 5600 includes a thrust generating housing 5607, which isconfigured to receive a thrust generating assembly 5608. The trustgenerating housing 5607 also includes a control and power receiver 5610and at least one or more pressure sensors 5614. In accordance with anexemplary embodiment, the one or more pressure sensors 5614 preferablycomprises a plurality of pressure sensors 5614, which is preferably atleast 3, and more preferably at least four pressure sensors 5614. It canbe appreciated that at least 3 pressure sensors 5614 are necessary toobtain a 3 axis (or 3 dimensional) reading. However, as little as onepressure sensor can be used if the application only requires a nominalmeasure of force.

As described herein, for example, the invention may be embodied insoftware (e.g., a plug-in or standalone software), in a machine (e.g., acomputer system, a microprocessor-based appliance, etc.) that includessoftware in memory, or in a non-transitory computer-readable storagemedium configured to carry out the control schemes (e.g., in aself-contained silicon device, a solid state memory, an optical disc, ora magnetic disc, among others).

While the foregoing specification teaches the principles of the presentinvention, with examples provided for the purpose of illustration only,it will be appreciated by one skilled in the art from reading thisdisclosure that various changes and modifications in form and detail canbe made, and equivalents employed, without departing from scope of theappended claims, which are to be given their full breadth.

What is claimed is:
 1. A replaceable structure for an air vehicle saidreplaceable structure configured to generate thrust and comprising: oneor more mounts, configured to be attached to the air vehicle; and athrust generating structure attached to each of the one or more mounts,wherein the thrust generating structure includes (i) a Nano MolecularSolid-State Electrodynamic Thruster (NMSET) element and (ii) a thrustgenerating module containing the NMSET element, the thrust generatingmodule having a thrust generating module housing enclosing the NMSETelement, and wherein the thrust generating module housing includes oneor more pressure sensors at the location of the NMSET element.
 2. Thereplaceable structure of claim 1, wherein each of the one or more mountsincludes at least one nest for receiving the thrust generatingstructure, and wherein the thrust generating module housing houses theNMSET element.
 3. The replaceable structure of claim 1, wherein each ofthe one or more mounts includes a plurality of nests for receiving thethrust generating structure, and wherein the thrust generating modulehousing houses the NMSET element.
 4. The replaceable structure of claim1, wherein the thrust generating structure comprises a thrust generatingstructure housing having top opening with a cavity therein, and aretainer plate having a bottom opening therein, and wherein the retainerplate fits with a recessed area on a bottom portion of the thrustgenerating structure housing.
 5. The replaceable structure of claim 4,wherein the thrust generating structure housing further includes acontrol and power connector.
 6. The replaceable structure of claim 5,wherein the thrust generating structure further includes a thrustgenerating assembly having the NMSET element therein and a control andpower receiver.
 7. The replaceable structure of claim 1, wherein the oneor more pressure sensors comprises at least three sensors.
 8. A methodof using the replaceable structure of claim 1 comprising: exposing thereplaceable structure to a source of ambient air at an ambienttemperature and pressure; and activating a means of heating and/orcooling alternating layers of the NMSET to form alternating hot and coldlayers such that the ambient air is propelled through the thrustgenerating structure.
 9. The method of claim 8, wherein each hot layeris hotter than the ambient temperature of the ambient air and each coldlayer is colder than the ambient temperature of the ambient air.
 10. Themethod of claim 8, wherein a mean temperature of all the hot and coldlayers is the same as the ambient temperature of the ambient air.